CN101784447B - Device and method for controlling the power supply of at least one aircraft maintenance actuator - Google Patents
Device and method for controlling the power supply of at least one aircraft maintenance actuator Download PDFInfo
- Publication number
- CN101784447B CN101784447B CN200880102555.XA CN200880102555A CN101784447B CN 101784447 B CN101784447 B CN 101784447B CN 200880102555 A CN200880102555 A CN 200880102555A CN 101784447 B CN101784447 B CN 101784447B
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- CN
- China
- Prior art keywords
- actuator
- state
- control unit
- sbr
- aircraft
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/54—Nozzles having means for reversing jet thrust
- F02K1/76—Control or regulation of thrust reversers
- F02K1/763—Control or regulation of thrust reversers with actuating systems or actuating devices; Arrangement of actuators for thrust reversers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings, or cowlings
- B64D29/08—Inspection panels for power plants
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D2221/00—Electric power distribution systems onboard aircraft
Abstract
The invention relates to a method and a device for controlling the power supply of at least one aircraft maintenance actuator (7) from an electrical power supply network (10) of the aircraft comprising means (14) for controlling the electrical power supply of at least one maintenance actuator, and means (15) for establishing communication between the control means and at least one control unit (16) allowing a user to control the operation of at least one actuator. The control means are designed to compare the state of at least one control unit with at least one reference state (SBR) and/or an abnormal state (SBE1, SBE2, SBE3) for switching-on purposes, and to prohibit the activation of the actuator if the state of the control unit is different from a reference state (SBR) or corresponds to an abnormal state (SBE1, SBE2, SBE3) when the power supply network is switched on.
Description
Technical field
The present invention relates to a kind of method and apparatus of the electric power supply for controlling at least one aircraft maintenance actuator, and a kind of turbojet engine nacelle that comprises the aircraft of such equipment.
Background technology
A kind of aircraft advances by many turbojets, each turbojet is accommodated in the machinery space, this machinery space also holds one group of assisted activation device, this group assisted activation device connects mutually with the running of turbojet, and carries out various functions when turbojet turns round or stops.These assisted activation devices comprise especially for the mechanical system that activates thrust reverser.
Machinery space has tubular structure usually, it comprises middle part, that an air system in the turbojet front portion, is designed to surround a fan of turbojet and is used for from turbojet guiding secondary streams and the rear portion that can hold thrust reverser, and machinery space finishes with an exhaust nozzle usually, and the outlet of this exhaust nozzle is positioned at the downstream of turbojet.
The Modern Engine cabin is designed to hold a pair of air-flow turbojet usually, and it can produce a secondary cold airflow by several pieces rotary fans, and this secondary cold airflow is added into from the main thermal current of the turbo-machine gained of turbojet.
Machinery space usually has an external structure and (is called external fixed structure (OFS), comprise one and be in the fairing of structure after the fan around turbojet self), it defines one for the ring duct (being also referred to as conduit) that flows with a concentric inner structure (being called internal fixing structure (IFS)), and its purpose is to guide the so-called secondary cold airflow of circulation outside turbojet.Primary air and secondary streams spray from turbojet by the machinery space rear portion.
Therefore, each propulsion system of aircraft comprises a machinery space and a turbojet, and be that the driving engine pillar hangs on the fixed sturcture of aircraft by an intermediary agency that is attached to turbojet or machinery space, for example, hang under the wings of an airplane or on the fuselage.
Machinery space comprises at least one pair of fairing, usually become by two semi-cylindrical in fact half hull shapes, each is on a side on a vertical vertical summetry plane of machinery space, and installed movably can between a control position and a maintenance position, launching, to allow near described turbojet.
These two fairings usually are installed into a hinge on the top (12 o'clock direction) around reverser and form the longitudinal axis and pivot.These fairings are maintained at an off position by the blocking device of placing along a knit line that is positioned at bottom (6 o'clock direction).
Machinery space can comprise for example a pair of fan fairing for covering turbojet fan part, and a pair of reverser fairing that comprises a thrust reverser and cover the turbojet rear portion.
Each fairing with at least one actuator for example a cylinder open, and staying open state with at least one connecting rod, this actuator and connecting rod respectively have the second end that a first end and that usually is fixed in turbojet is fixed in fairing.
As everyone knows, actuator can be produced with the hydraulic actuator form.
Same well-known, change some part of machinery space with electromechanical actuator, such as the thrust reverser fairing, as described in document EP 0843089.
Described actuator is controlled by the control unit that a user can contact, and described control unit comprises at least one actuator control button.
The maintenance electrical network of described maintenance actuator power supply is powered on when the aircraft outage usually, and this is, when aircraft on the ground, when engine stop or when not detecting aboard the combustion fire.
One of control button of control unit is possible, for example owing to block, and is depressed always.
In such a case, have following risk: the maintenance supply network will be opened fairing once powering on immediately unfolded actuator, and when fairing was locked, this may cause the early stage infringement of driving engine and actuator electronics.When fairing was not locked, such expansion also may threaten personal safety because of the unexpected displacement that fairing produces.In addition, the expansion of actuator does not need to be ordered and can carry out.
It should be noted that the risk of this expansion also is prevalent in the aircraft maintenance actuator of other types except machinery space fairing actuator.
Summary of the invention
The present invention's purpose is to avoid being powered on when maintenance supply network one, and maintenance actuator just launches in without the situation of user's order.
For this reason, the present invention's theme be a kind of for control from the supply network of the aircraft equipment to the electric power supply of at least one maintenance actuator of aircraft, it comprises:
-be used for control to the device of the electric power supply of at least one maintenance actuator,
-be used between described control setup and at least one control unit, setting up communicate by letter controlling the device that described at least one actuator operates with the permission user,
It is characterized in that
Described control setup is designed to when supply network is powered on the state of at least one control unit and at least one reference state for powering on and/or error state be compared, if and described control unit state is different from reference state or corresponding to error state, forbids the starting of described actuator.
According to arrangement of the present invention, when not being in reference to normal condition after described control unit is powering on, the running of electric actuator is under an embargo.
These arrange particularly can test example such as the control unit button that is depressed owing to blocking always and prevent that it from causing that actuator is ordered without the user and being shifted.
Therefore the use of described actuator is by safe.
Advantageously, described control setup is designed to allow the starting of described actuator when described control unit state is modified to the reference state that turns back to for powering on.
According to an embodiment, the state that described one or more reference states do not order actuator to move corresponding to described control unit.
The invention still further relates to a kind of aircraft turbojet engine nacelle, it comprises at least one maintenance actuator, a control unit and an equipment as indicated above.
According to a kind of possibility, described equipment is arranged to one and is used for described actuator power supply and monitors the unit of described actuator.
According to another kind of possibility, described equipment is arranged on the described actuator.
Another theme of the present invention is that a kind of control is from the method for aircraft supply network to the electric power supply of at least one aircraft maintenance actuator, it comprises, when supply network is powered on, one step: at least one control unit state and at least one reference state for powering on and/or error state are compared, if and described control unit state is different from reference state or corresponding to error state, forbids the starting of described actuator.
Description of drawings
In any case, representing the accompanying drawing of an embodiment of this equipment by means of hereinafter describing simultaneously with reference to given with unrestricted example form, the present invention will be expressly understood.
Fig. 1 is that fan and reverser fairing are opened from the full view of lower perspective one machinery space and a turbojet.
Fig. 2 is the machinery space of Fig. 1 and a front elevation of turbojet.
Fig. 3 is the scheme drawing of one equipment according to the present invention.
Fig. 4 is when supply network is powered on, the scheme drawing of a reference state of a control unit.
Fig. 5 a to 5c is when supply network is powered on, the scheme drawing of the error state of described control unit.
The specific embodiment
As depicted in figs. 1 and 2, one aircraft nacelle 2 in known manner, as mentioned above, comprise a pair of fan fairing 3 for covering turbojet fan part 4, and a pair of reverser fairing 5 that comprises a thrust reverser and cover turbojet rear portion 6.
These fairings 3,5 are driven and mobile between their closed and opened positions by an actuator, and described actuator comprises, and a for example dynamo-electric cylinder 7, and these fairings 3,5 is maintained at open position by a connecting rod 8, shown in Fig. 2 is obvious.
According to the present invention, machinery space comprises an equipment 9, and what it was used for that control as Fig. 3 represent one keeps in repair supply network to the electric power supply of maintenance actuator 7.
This equipment is placed in an actuator electric power supply and the monitoring means.
Described equipment 9 comprises a first order 12, and a supply network 10 of aircraft is connected to the first order 12, and described supply network provides three plase alternating current with usual way.This first order 12 comprises especially one and exchanges (AC) to direct current (DC) electric pressure converter, and described conv comprises a voltage rectifier and a voltage step assembly, and direct current (DC) voltage of a 400V for example is provided.
Control convenience 9 also comprises a power level 13, is designed to 7 power supplies of at least one maintenance actuator, and described at least one maintenance actuator 7 downstream link to described equipment.Especially, the second power level 13 comprises one first direct current (DC) voltage transitions that will be derived from the described first order to the conv that is used for one second direct current (DC) voltage of an actuator 7 power supplies.
Described equipment further comprises first and second grade 12 of control, 13 device, and it is comprised of a microcontroller 14.
Fig. 4 and Fig. 5 a to Fig. 5 c are the control units 16 that is in the different conditions.
Described control unit 16 has two control button 17A and 17B, corresponds respectively to open the fairing 3 that is driven by actuator 7,5 order, and closes the fairing 3 that is driven by actuator, 5 order.
These two button 17A, 17B are near two electrical pickofves, in order to provide an electric signal by the electric wire 18 that forms communicator 15 to microcontroller 14 when they are depressed.
Fig. 4 is depicted in two button 17A, 17B of dead position.Do not have button to be depressed, therefore, do not have the actuator movement directive to be sent by described control unit.This arrangement of described control unit thus, when supply network is powered on, can be allowed to powering on of described actuator by described microcontroller corresponding to reference state SBR.
It is not corresponding to reference state but corresponding to state SBE1, SBE2, the SBE3 of error state that Fig. 5 a to Fig. 5 c describes three of described control unit.Especially, in the state SBE1 corresponding to Fig. 5 a, fairing is opened button 17A and is depressed, and this opens fairing corresponding to sending an order to a direction movement actuator 7, and this moment, X button 17B was in its quiescence.
In the state SBE2 of corresponding diagram 5b, fairing X button 17B is depressed, and order of this corresponding transmission is closed to cause fairing to a direction movement actuator, and open button 17A and be in its quiescence this moment.
In the state SBE3 of corresponding diagram 5c, button 17A is closed and opened to fairing and 17B is depressed, and this does not correspond to an actuator commands that conforms to.
Therefore, as shown in Figure 6, after E0 that supply network is powered on, a kind of enforcement by described equipment comprises a first step E1 with the method for control power supply: with the state of at least one control unit 16 and at least one reference state SBR for powering on relatively.
If the state of described control unit is corresponding with reference state SBR, microcontroller 14 powers on to described actuator at a second step E2 of described method so, then waits for the control command that is derived from control unit 16 at a third step E3.
In reverse situation, that is, if control unit 16 is in above with reference in the state of figure 5a in the described state SBE1 of 5c, SBE2, the SBE3, so powering on of actuator is not allowed to, because described control unit state is different from a reference state.
The step e 1 of described method is repeated, until described control unit state is modified to the reference state SBR that is back to for powering on.
According to a version, described equipment is arranged directly on the described actuator.
According to another version, same control convenience can be monitored powering on of a plurality of actuators by the power-up state that checks a plurality of control units.
Much less, the present invention does not limit what above with the single embodiment of example formal description, antithesis, contains all changes form.
Should be specifically noted that the fairing of other types can be by the actuator control of described power devices.
Claims (9)
1. one kind is used for control from the supply network (10) of the aircraft equipment (9) to the electric power supply of at least one maintenance actuator (7) of described aircraft, and it comprises:
-be used for control to the device (14) of the electric power supply of at least one maintenance actuator (7),
-be used between described control setup (14) and at least one control unit (16), setting up communicate by letter controlling the device (15) that at least one actuator (7) operates with the permission user,
It is characterized in that
Described control setup (14) is designed to when described supply network (10) is powered on the state of at least one control unit (16) and at least one reference state (SBR) and/or error state (SBE1 for powering on, SBE2, SBE3) relatively, if and the state of described control unit (16) is different from reference state (SBR) or corresponding to error state (SBE1, SBE2, SBE3), then forbid the starting of described actuator.
2. equipment according to claim 1 (9), wherein said control setup (14) is designed to allow the starting of described actuator when the state of described control unit (16) is modified to the reference state (SBR) that is back to for powering on.
3. according to the described equipment of arbitrary claim (9) in the aforementioned claim, wherein said one or more reference states (SBR) are not ordered the mobile state of described actuator (7) corresponding to described control unit.
4. an aircraft turbojet engine nacelle (2), it comprises at least one maintenance actuator (7), a control unit (16) and one according to the described equipment of arbitrary claim (9) in the aforementioned claim.
5. machinery space according to claim 4 (2), wherein said equipment (9) are arranged to one and are used for described actuator (7) is powered and monitored the unit of described actuator (7).
6. machinery space according to claim 4 (2), wherein said equipment (9) is arranged on the described actuator (7).
7. one kind is used for control from the supply network (10) of the aircraft method to the electric power supply of at least one maintenance actuator (7) of described aircraft, comprise, when described supply network is powered on (E0), a step (E 1), with the state of at least one control unit and at least one reference state (SBR) and/or error state (SBE1 for powering on, SBE2, SBE3) relatively, if and the state of described control unit (16) is different from reference state (SBR) or corresponding to error state (SBE1, SBE2, SBE3), then forbid the starting of described actuator (7).
8. method according to claim 7, the starting of wherein said actuator (7) is allowed to when the state of described control unit (16) is modified to the reference state (SBR) that is back to for powering on.
9. according to the described method of arbitrary claim in aforementioned claim 7 and 8, wherein said one or more reference states (SBR) are not ordered the mobile state of described actuator (7) corresponding to described control unit.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR0705929 | 2007-08-20 | ||
| FR0705929A FR2920142B1 (en) | 2007-08-20 | 2007-08-20 | DEVICE AND METHOD FOR CONTROLLING THE SUPPLY OF AT LEAST ONE MAINTENANCE ACTUATOR OF AN AIRCRAFT |
| PCT/FR2008/000742 WO2009024656A1 (en) | 2007-08-20 | 2008-06-02 | Device and method for controlling the power supply of at least one aircraft maintenance actuator |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101784447A CN101784447A (en) | 2010-07-21 |
| CN101784447B true CN101784447B (en) | 2013-03-27 |
Family
ID=39246767
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200880102555.XA Expired - Fee Related CN101784447B (en) | 2007-08-20 | 2008-06-02 | Device and method for controlling the power supply of at least one aircraft maintenance actuator |
Country Status (11)
| Country | Link |
|---|---|
| US (1) | US8684305B2 (en) |
| EP (1) | EP2181039B1 (en) |
| CN (1) | CN101784447B (en) |
| AT (1) | ATE501934T1 (en) |
| BR (1) | BRPI0813608A2 (en) |
| CA (1) | CA2693352C (en) |
| DE (1) | DE602008005602D1 (en) |
| ES (1) | ES2361384T3 (en) |
| FR (1) | FR2920142B1 (en) |
| RU (1) | RU2463215C2 (en) |
| WO (1) | WO2009024656A1 (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR101396974B1 (en) | 2007-07-23 | 2014-05-20 | 엘지전자 주식회사 | Portable terminal and method for processing call signal in the portable terminal |
| FR2920143B1 (en) * | 2007-08-20 | 2010-01-22 | Aircelle Sa | DEVICE FOR CONTROLLING HOUSING MAINTENANCE ACTUATORS OF A TURBOREACTOR NACELLE |
| US20110186096A1 (en) * | 2010-02-02 | 2011-08-04 | Gas Turbine Efficiency Sweden Ab | Aircraft maintenance unit |
| US9783315B2 (en) * | 2012-02-24 | 2017-10-10 | Rohr, Inc. | Nacelle with longitudinal translating cowling and rotatable sleeves |
| US9217390B2 (en) | 2012-06-28 | 2015-12-22 | United Technologies Corporation | Thrust reverser maintenance actuation system |
| US20140032002A1 (en) * | 2012-07-30 | 2014-01-30 | The Boeing Company | Electric system stabilizing system for aircraft |
| US9701414B2 (en) * | 2013-09-16 | 2017-07-11 | Honeywell International Inc. | Aircraft engine cowl door movement control system and method |
| US9764853B2 (en) * | 2015-04-01 | 2017-09-19 | The Boeing Company | Motionless flight control surface skew detection system |
Family Cites Families (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US622963A (en) * | 1899-04-11 | Necktie-fastener | ||
| US5058873A (en) * | 1978-01-04 | 1991-10-22 | Datacard Corporation | Data card and mailer inserter system |
| RU1766020C (en) * | 1989-12-20 | 1994-08-15 | Авиационный комплекс им.С.В.Ильюшина | Flying vehicle engine nacelle flap |
| FR2755730B1 (en) | 1996-11-14 | 1999-01-08 | Hispano Suiza Sa | ELECTRICAL CONTROL SYSTEM FOR A TURBOREACTOR DRIVE INVERTER |
| US5923145A (en) * | 1997-08-15 | 1999-07-13 | S-B Power Tool Company | Controller for variable speed motor |
| US6227489B1 (en) * | 1998-05-15 | 2001-05-08 | Koito Industries, Ltd. | Aircraft seat apparatus |
| JP2001320620A (en) * | 2000-05-12 | 2001-11-16 | Canon Inc | Image pickup device, its control method and storage medium |
| FR2811780B1 (en) * | 2000-07-13 | 2002-08-30 | Aerospatiale Matra Airbus | METHOD AND DEVICE FOR CONTROLLING MANEUVERING DEVICES OF AN AIRCRAFT WITH ELECTRIC BACKUP MODULES |
| US6439504B1 (en) * | 2001-06-15 | 2002-08-27 | Honeywell International, Inc. | System and method for sustaining electric power during a momentary power interruption in an electric thrust reverser actuation system |
| US6622963B1 (en) * | 2002-04-16 | 2003-09-23 | Honeywell International Inc. | System and method for controlling the movement of an aircraft engine cowl door |
| US6883394B2 (en) * | 2002-10-15 | 2005-04-26 | Borgwarner, Inc. | Method for controlling the positioning of the synchronizers of a dual clutch transmission |
| FR2887301B1 (en) * | 2005-06-16 | 2007-08-31 | Aircelle Sa | ELECTRONIC CONTROL SYSTEM FOR NACELLE |
| FR2920143B1 (en) * | 2007-08-20 | 2010-01-22 | Aircelle Sa | DEVICE FOR CONTROLLING HOUSING MAINTENANCE ACTUATORS OF A TURBOREACTOR NACELLE |
-
2007
- 2007-08-20 FR FR0705929A patent/FR2920142B1/en not_active Expired - Fee Related
-
2008
- 2008-06-02 WO PCT/FR2008/000742 patent/WO2009024656A1/en active Application Filing
- 2008-06-02 US US12/673,692 patent/US8684305B2/en not_active Expired - Fee Related
- 2008-06-02 BR BRPI0813608-4A2A patent/BRPI0813608A2/en not_active IP Right Cessation
- 2008-06-02 CN CN200880102555.XA patent/CN101784447B/en not_active Expired - Fee Related
- 2008-06-02 DE DE602008005602T patent/DE602008005602D1/en active Active
- 2008-06-02 AT AT08805631T patent/ATE501934T1/en not_active IP Right Cessation
- 2008-06-02 CA CA2693352A patent/CA2693352C/en not_active Expired - Fee Related
- 2008-06-02 EP EP08805631A patent/EP2181039B1/en not_active Not-in-force
- 2008-06-02 ES ES08805631T patent/ES2361384T3/en active Active
- 2008-06-02 RU RU2010109789/11A patent/RU2463215C2/en not_active IP Right Cessation
Also Published As
| Publication number | Publication date |
|---|---|
| BRPI0813608A2 (en) | 2014-12-30 |
| CA2693352C (en) | 2015-02-24 |
| FR2920142A1 (en) | 2009-02-27 |
| RU2010109789A (en) | 2011-09-27 |
| CA2693352A1 (en) | 2009-02-26 |
| DE602008005602D1 (en) | 2011-04-28 |
| RU2463215C2 (en) | 2012-10-10 |
| US20100201190A1 (en) | 2010-08-12 |
| CN101784447A (en) | 2010-07-21 |
| WO2009024656A1 (en) | 2009-02-26 |
| ATE501934T1 (en) | 2011-04-15 |
| US8684305B2 (en) | 2014-04-01 |
| EP2181039A1 (en) | 2010-05-05 |
| EP2181039B1 (en) | 2011-03-16 |
| ES2361384T3 (en) | 2011-06-16 |
| FR2920142B1 (en) | 2009-09-18 |
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Granted publication date: 20130327 Termination date: 20160602 |